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GOE 611 AIRFOIL (goe611-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: GOE 611 AIRFOIL (goe611-il)
Reynolds number: 1,000,000
Max Cl/Cd: 125.62 at α=4.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe611-il-1000000.txt
Download as CSV file: xf-goe611-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 611 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.1696   0.09936   0.09767  -0.0684   0.9368   0.0122
  -9.750  -0.1670   0.09602   0.09421  -0.0693   0.9046   0.0122
  -9.500  -0.1638   0.09257   0.09066  -0.0690   0.8818   0.0124
  -9.250  -0.1567   0.09009   0.08810  -0.0695   0.8647   0.0125
  -9.000  -0.1498   0.08748   0.08542  -0.0705   0.8518   0.0126
  -8.750  -0.1430   0.08475   0.08263  -0.0719   0.8411   0.0128
  -8.500  -0.1364   0.08185   0.07970  -0.0735   0.8324   0.0130
  -8.250  -0.1303   0.07886   0.07666  -0.0754   0.8243   0.0133
  -8.000  -0.1246   0.07563   0.07343  -0.0778   0.8169   0.0137
  -7.750  -0.1213   0.07231   0.07006  -0.0807   0.8097   0.0141
  -7.250  -0.0947   0.05988   0.05751  -0.0983   0.7970   0.0153
  -7.000  -0.0796   0.05496   0.05248  -0.1025   0.7917   0.0153
  -6.750  -0.0639   0.04992   0.04733  -0.1058   0.7862   0.0153
  -6.500  -0.0538   0.04553   0.04283  -0.1077   0.7808   0.0157
  -6.250  -0.0348   0.04362   0.04086  -0.1086   0.7755   0.0159
  -6.000  -0.0144   0.04141   0.03856  -0.1097   0.7699   0.0164
  -5.750   0.0071   0.03875   0.03576  -0.1107   0.7644   0.0172
  -5.500   0.0347   0.03309   0.02972  -0.1115   0.7595   0.0189
  -5.250   0.0558   0.02897   0.02530  -0.1116   0.7539   0.0190
  -5.000   0.0750   0.02499   0.02103  -0.1116   0.7484   0.0187
  -4.750   0.0989   0.02419   0.02019  -0.1121   0.7422   0.0200
  -4.500   0.1244   0.02336   0.01926  -0.1123   0.7355   0.0210
  -4.250   0.1539   0.02159   0.01705  -0.1114   0.7294   0.0233
  -4.000   0.1761   0.01788   0.01309  -0.1114   0.7226   0.0219
  -3.750   0.2030   0.01685   0.01185  -0.1113   0.7154   0.0247
  -3.500   0.2302   0.01652   0.01147  -0.1116   0.7063   0.0261
  -3.250   0.2602   0.01723   0.01195  -0.1112   0.6959   0.0288
  -2.250   0.3690   0.01165   0.00556  -0.1108   0.6521   0.0298
  -2.000   0.3964   0.01105   0.00488  -0.1107   0.6403   0.0304
  -1.750   0.4239   0.01083   0.00463  -0.1108   0.6278   0.0318
  -1.500   0.4515   0.01038   0.00410  -0.1107   0.6152   0.0318
  -1.250   0.4788   0.01004   0.00367  -0.1106   0.6012   0.0318
  -1.000   0.5062   0.00978   0.00334  -0.1106   0.5878   0.0321
  -0.750   0.5337   0.00960   0.00311  -0.1106   0.5760   0.0328
  -0.500   0.5611   0.00947   0.00292  -0.1106   0.5649   0.0337
  -0.250   0.5887   0.00935   0.00273  -0.1106   0.5542   0.0342
   0.000   0.6165   0.00925   0.00259  -0.1106   0.5440   0.0347
   0.250   0.6441   0.00920   0.00248  -0.1107   0.5346   0.0352
   0.500   0.6719   0.00917   0.00241  -0.1108   0.5252   0.0356
   0.750   0.6998   0.00914   0.00233  -0.1109   0.5165   0.0360
   1.000   0.7272   0.00909   0.00221  -0.1109   0.5075   0.0382
   1.250   0.7553   0.00907   0.00217  -0.1111   0.4993   0.0400
   1.500   0.7827   0.00912   0.00218  -0.1111   0.4910   0.0421
   1.750   0.8106   0.00916   0.00218  -0.1112   0.4827   0.0444
   2.000   0.8348   0.00782   0.00240  -0.1115   0.4749   0.7195
   2.250   0.8621   0.00734   0.00252  -0.1112   0.4657   1.0000
   2.500   0.8890   0.00747   0.00258  -0.1111   0.4571   1.0000
   2.750   0.9154   0.00763   0.00266  -0.1110   0.4469   1.0000
   3.000   0.9425   0.00775   0.00274  -0.1110   0.4381   1.0000
   3.250   0.9691   0.00790   0.00284  -0.1109   0.4296   1.0000
   3.500   0.9957   0.00805   0.00293  -0.1109   0.4201   1.0000
   3.750   1.0223   0.00821   0.00304  -0.1108   0.4106   1.0000
   4.000   1.0483   0.00839   0.00317  -0.1107   0.4002   1.0000
   4.250   1.0744   0.00858   0.00331  -0.1106   0.3894   1.0000
   4.500   1.1004   0.00876   0.00344  -0.1104   0.3788   1.0000
   4.750   1.1259   0.00897   0.00360  -0.1102   0.3678   1.0000
   5.000   1.1510   0.00921   0.00378  -0.1100   0.3558   1.0000
   5.250   1.1757   0.00946   0.00397  -0.1096   0.3426   1.0000
   5.500   1.1993   0.00978   0.00420  -0.1091   0.3233   1.0000
   5.750   1.2213   0.01019   0.00448  -0.1083   0.3008   1.0000
   6.000   1.2416   0.01070   0.00483  -0.1073   0.2719   1.0000
   6.250   1.2597   0.01133   0.00525  -0.1058   0.2377   1.0000
   6.500   1.2750   0.01211   0.00579  -0.1039   0.1986   1.0000
   6.750   1.2817   0.01333   0.00665  -0.1005   0.1383   1.0000
   7.000   1.2998   0.01382   0.00708  -0.0991   0.1280   1.0000
   7.250   1.3180   0.01425   0.00748  -0.0976   0.1216   1.0000
   7.500   1.3369   0.01457   0.00781  -0.0963   0.1188   1.0000
   7.750   1.3554   0.01493   0.00819  -0.0949   0.1164   1.0000
   8.000   1.3719   0.01539   0.00864  -0.0932   0.1122   1.0000
   8.250   1.3880   0.01590   0.00914  -0.0915   0.1072   1.0000
   8.500   1.4082   0.01621   0.00949  -0.0905   0.1046   1.0000
   8.750   1.4245   0.01673   0.00999  -0.0890   0.0982   1.0000
   9.000   1.4400   0.01731   0.01052  -0.0874   0.0863   1.0000
   9.500   1.4287   0.02108   0.01390  -0.0786   0.0152   1.0000
   9.750   1.4420   0.02193   0.01481  -0.0771   0.0141   1.0000
  10.000   1.4541   0.02291   0.01585  -0.0755   0.0132   1.0000
  10.250   1.4639   0.02407   0.01708  -0.0738   0.0123   1.0000
  10.500   1.4704   0.02553   0.01864  -0.0719   0.0114   1.0000
  10.750   1.4818   0.02668   0.01984  -0.0706   0.0111   1.0000
  11.000   1.4919   0.02796   0.02118  -0.0693   0.0107   1.0000
  11.250   1.5007   0.02937   0.02265  -0.0680   0.0102   1.0000
  11.500   1.5082   0.03092   0.02428  -0.0667   0.0097   1.0000
  11.750   1.5141   0.03266   0.02608  -0.0653   0.0093   1.0000
  12.000   1.5165   0.03475   0.02825  -0.0638   0.0090   1.0000
  12.250   1.5126   0.03746   0.03109  -0.0621   0.0086   1.0000
  12.500   1.5136   0.03984   0.03356  -0.0608   0.0084   1.0000
  12.750   1.5187   0.04188   0.03568  -0.0600   0.0083   1.0000
  13.000   1.5219   0.04417   0.03804  -0.0591   0.0081   1.0000
  13.250   1.5233   0.04671   0.04067  -0.0583   0.0079   1.0000
  13.500   1.5237   0.04944   0.04349  -0.0577   0.0077   1.0000
  13.750   1.5234   0.05235   0.04649  -0.0571   0.0075   1.0000
  14.000   1.5219   0.05545   0.04967  -0.0567   0.0073   1.0000
  14.250   1.5198   0.05870   0.05301  -0.0564   0.0072   1.0000
  14.500   1.5176   0.06206   0.05645  -0.0563   0.0070   1.0000
  14.750   1.5139   0.06567   0.06015  -0.0562   0.0069   1.0000
  15.000   1.5091   0.06946   0.06403  -0.0563   0.0067   1.0000
  15.250   1.5000   0.07389   0.06855  -0.0565   0.0066   1.0000
  15.500   1.4872   0.07894   0.07371  -0.0569   0.0064   1.0000
  15.750   1.4716   0.08445   0.07934  -0.0575   0.0063   1.0000
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